CN106043662A - Aircraft rear structure - Google Patents
Aircraft rear structure Download PDFInfo
- Publication number
- CN106043662A CN106043662A CN201610206268.XA CN201610206268A CN106043662A CN 106043662 A CN106043662 A CN 106043662A CN 201610206268 A CN201610206268 A CN 201610206268A CN 106043662 A CN106043662 A CN 106043662A
- Authority
- CN
- China
- Prior art keywords
- aft
- aircraft
- pressure bulkhead
- spar
- attachment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000003381 stabilizer Substances 0.000 claims abstract description 25
- 230000003993 interaction Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/10—Bulkheads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
- Tires In General (AREA)
Abstract
The invention provides an aircraft rear structure (10) comprising a substantially flat rear pressure bulkhead (11), with a first side and a second side, opposite to the first side. The aircraft rear structure (10) also comprises a horizontal stabilizer (21) and a vertical stabilizer (1) which in turn comprises a first spar (2) and a second spar (3). The first spar (2) is attached to a first attachment zone (41) of the second side of the rear pressure bulkhead (11) by means of first attaching means (5, 6), and the second spar (3) is attached to a second attachment zone (42) of the second side of the rear pressure bulkhead (11) by means of second attaching means (7, 8). The second attachment zone (42) being different from the first attachment zone (41).
Description
Technical Field
The present invention relates to the field of aircraft components, and more particularly to aircraft aft structures.
Background
Several solutions are known for the arrangement of elements included in the rear region of an aircraft, in particular for the arrangement of vertical stabilizers to the fuselage.
This joint must satisfy all the dynamic requirements that are normally experienced by aircraft, including shear forces due to aerodynamic loads generated in the vertical stabilizer, which is normally attached by one of its ends to a region in the upper part of the fuselage.
In the aircraft known from the prior art, this attachment is achieved by means of a set of fittings provided on an upper shell structure arranged in the fuselage.
The shell structure is in turn attached to several frames of the fuselage and, as a result, the loads generated in the fittings are transferred to the primary structure of the aircraft.
This attachment has been used in aircraft for decades, but means an increase in the weight of the fuselage structure, due to the safety standards that must be met, and due to the fact that: fittings typically work in shear and need to be larger and stronger to withstand these loads.
Disclosure of Invention
The present invention provides a solution to the aforementioned problems by an aircraft tail arrangement according to one aspect of the invention and an aircraft according to another aspect of the invention. All of the features described in this specification (including the claims, specification and drawings) may be combined in any combination, except combinations where such features are mutually exclusive.
According to a first aspect, the invention provides an aircraft rear structure comprising:
a substantially planar aft pressure bulkhead having a first side and a second side opposite the first side,
a horizontal stabilizer is arranged on the upper portion of the frame,
a vertical stabilizer, which in turn comprises a first spar and a second spar,
wherein,
the first spar is attached to a first attachment region of a second side of the aft pressure bulkhead by a first attachment device,
a second spar is attached to a second attachment region of a second side of the aft pressure bulkhead by a second attachment device,
the second attachment region is different from the first attachment region.
The attachment device is an element configured to attach two components. In particular, these attachment means can be fittings, bolts and combinations thereof or any similar elements performing the same technical function.
Advantageously, the aircraft rear structure according to the invention is adapted to be attached to the rest of the aircraft without the use of a shell structure. This saves weight on the aircraft and redistributes the load to the entire aft pressure bulkhead, rather than concentrating the load transfer in a smaller area located in the aft crown of the aircraft.
The aft pressure bulkhead is one of the surfaces that encloses the pressurized region of the aircraft. The aft pressure bulkhead is located in the aft portion of the aircraft in a manner that is generally perpendicular to the fuselage axis.
In embodiments known in the prior art, the aft pressure bulkhead does not involve attachment to vertical stabilizers, since in these cases the vertical stabilizers are attached to a housing arranged in the periphery of the fuselage and the aft pressure bulkhead is arranged to cover the cross section of said fuselage. Thus, there is no interaction between these two elements as known in the prior art.
This embodiment eliminates the weight for one element of the aircraft and allows the remainder of the aircraft rear structure to dispense with structural requirements.
In a particular embodiment, the first attachment region corresponds to an upper region of the aft pressure bulkhead and the second attachment region corresponds to a lower region of the aft pressure bulkhead.
This optimal solution allows a better management of the load distribution along the aft pressure bulkhead.
In a particular embodiment, the first attachment means comprises a first corner fitting and a first rear fitting, and the second attachment means comprises a second corner fitting and a second rear fitting.
A corner fitting is an element comprising two bearing surfaces forming an angle. The corner fitting is used to attach two different elements that form an angle between them.
The rear fitting is such an element: the element is arranged on the back side of the element, the back side of which has been attached to another element, thus being fixedly attached. The rear fitting does not need to comply with any particular conditions, since the rear fitting only holds a fixing element, typically a bolt or the like. In a particular embodiment, the rear fitting has a shape that allows it to be placed in contact with other surfaces, thus reinforcing its position.
In a particular embodiment, the first corner fitting attaches the first spar to the second side of the aft pressure bulkhead by means of first fastening means, and the first aft fitting secures these first fastening means from the first side of the aft pressure bulkhead.
In a particular embodiment, the second corner fittings attach the second spar to the second side of the aft pressure bulkhead by means of second fastening means, and the second aft fittings secure these second fastening means from the first side of the aft pressure bulkhead.
In a second aspect of the invention, the invention provides an aircraft comprising an aircraft aft structure according to the first aspect of the invention.
Drawings
These and other characteristics and advantages of the present invention will be clearly understood from the detailed description made of the invention, which is given by way of example only and not as a limitation thereof, with reference to the accompanying drawings, and which is made apparent in accordance with a preferred embodiment of the present invention.
Fig. 1 shows an aircraft rear structure according to the prior art.
Fig. 2 shows an aircraft rear structure according to the invention.
Fig. 3 shows a detail of the attachment of a vertical stabilizer in the aircraft rear structure according to the invention.
Fig. 4 shows a further detail of the attachment of a vertical stabilizer in the aircraft rear structure according to the invention.
Fig. 5 shows a further detail of the attachment of a vertical stabilizer in the aircraft rear structure according to the invention.
Figure 6 shows an aircraft comprising an aircraft rear structure according to the invention.
Detailed Description
Having outlined the objects of the present invention, specific non-limiting embodiments will be described hereinafter.
Fig. 1 shows an aircraft rear structure 110 according to the prior art. In this figure, the vertical stabilizer 101 is attached to a housing structure 106, which housing structure 106 is arranged on the top part of the fuselage. Both the front spar 102 and the rear spar 103 of the vertical stabilizer 101 according to the prior art are attached to the shell structure 106 together with several cross fittings 107. This shell structure 106 comprises several fittings that receive the loads generated in the vertical stabilizer 101 and transfer them to the shell structure 106 and subsequently to the fuselage.
Fig. 2 shows an aircraft rear structure 10 according to the invention. The aircraft rear structure 10 comprises:
a substantially planar aft pressure bulkhead 11, the substantially planar aft pressure bulkhead 11 having a first side and a second side opposite the first side,
the horizontal stabilizer (21) is provided with a horizontal stabilizer,
a vertical stabilizer 1, which vertical stabilizer 1 in turn comprises a first spar 2 and a second spar 3,
wherein,
the first spar 2 is attached to a first attachment area 41 of the second side of the aft pressure bulkhead 11 by means of first attachment means 5, 6,
the second spar 3 is attached to a second attachment area 42 of a second side of the aft pressure bulkhead 11 by means of second attachment means 7, 8,
the second attachment area 42 is different from the first attachment area 41.
In this figure, it can be observed how the first attachment zone 41 corresponds to an upper region of the aft pressure bulkhead 11, and the second attachment zone 42 corresponds to a lower region of the aft pressure bulkhead 11.
In this figure, a central corner fitting 14 on the second side of the aft pressure bulkhead 11 is also observed.
Thus, the vertical stabilizer is not attached to the housing comprising a plurality of heavy fittings, but to the aft pressure bulkhead 11. The interaction between the attachment of the first and second spars of the vertical stabilizer and the positioning of the aft pressure bulkhead allows for symbiotic reinforcement of the two attachments.
In a particular embodiment, the attachment between the spar of the vertical stabilizer and the aft pressure bulkhead is performed by a first attachment device and a second attachment device. Fig. 3 shows a detail of a first attachment device used in a particular embodiment of the aircraft aft structure according to the invention. In this figure, it can be seen that: the first attachment means comprise a first corner fitting 5 and a first aft fitting 6, how the first corner fitting 5 attaches the first spar 2 to the second side of the aft pressure bulkhead 11 by means of first fastening means (not shown), and how the first aft fitting 6 secures these first fastening means from the first side of the aft pressure bulkhead 11. In this figure, a central corner fitting 14 on the second side of the aft pressure bulkhead 11 is also observed.
Fig. 4 shows a detail of the second attachment means, which in turn comprises a second corner fitting 7 and a second rear fitting 8. The second corner fittings 7 attach the second spar 3 to the second side of the aft pressure bulkhead 11 by means of second fastening means (not shown), and the second aft fittings 8 fix these second fastening means from the first side of the aft pressure bulkhead 11.
Fig. 5 shows a view of an aircraft rear structure according to the invention. In this case, the second side of the aft pressure bulkhead 11 can be seen in this view instead of the first side, which is seen in fig. 3 and 4. In this figure, the first corner fitting 5 and the first aft fitting 6 are seen attaching the first spar 2 to a second side of the aft pressure bulkhead 11, and the second corner fitting 7 and the second aft fitting 8 are seen attaching the second spar 3 to a second side of the aft pressure bulkhead 11. Furthermore, a central corner fitting 14 on the second side of the aft pressure bulkhead 11 is also observed.
Fig. 6 shows an aircraft 100 comprising an aircraft rear structure 10 according to the invention. It can be observed that no shell structure is required since the loads are directly transferred from the first and second spars of the vertical stabilizer to the two different regions of the aft pressure bulkhead, thereby reducing the shear stress at the top of the fuselage.
Claims (6)
1. An aircraft aft structure (10), comprising:
a substantially planar aft pressure bulkhead (11), the substantially planar aft pressure bulkhead (11) having a first side and a second side opposite the first side,
a horizontal stabilizer (21),
a vertical stabilizer (1), said vertical stabilizer (1) in turn comprising a first spar (2) and a second spar (3),
wherein,
the first spar (2) is attached to a first attachment region (41) of the second side of the aft pressure bulkhead (11) by a first attachment device (5, 6),
the second spar (3) is attached to a second attachment region (42) of the second side of the aft pressure bulkhead (11) by a second attachment device (7, 8),
the second attachment region (42) is different from the first attachment region (41).
2. The aircraft aft structure (10) according to claim 1, wherein the first attachment region (41) corresponds to an upper region of the aft pressure bulkhead (11) and the second attachment region (42) corresponds to a lower region of the aft pressure bulkhead (11).
3. The aircraft aft structure (10) according to any one of the preceding claims, wherein the first attachment means comprises a first corner fitting (5) and a first aft fitting (6), and the second attachment means comprises a second corner fitting (7) and a second aft fitting (8).
4. The aircraft aft structure (10) according to claim 3, wherein the first corner fitting (5) attaches the first spar (2) to the second side of the aft pressure bulkhead (11) by means of first fastening means, and the first aft fitting (6) secures these first fastening means from the first side of the aft pressure bulkhead (11).
5. The aircraft aft structure (10) according to claim 3 or 4, wherein the second corner fitting (7) attaches the second spar (3) to the second side of the aft pressure bulkhead (11) by means of second fastening means, and the second aft fitting (8) secures these second fastening means from the first side of the aft pressure bulkhead (11).
6. An aircraft (100), the aircraft (100) comprising an aircraft aft structure (10) according to any one of the preceding claims.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP15382169.9 | 2015-04-08 | ||
| EP15382169.9A EP3078586B1 (en) | 2015-04-08 | 2015-04-08 | Aircraft rear structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106043662A true CN106043662A (en) | 2016-10-26 |
Family
ID=53039366
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610206268.XA Pending CN106043662A (en) | 2015-04-08 | 2016-04-05 | Aircraft rear structure |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US10046848B2 (en) |
| EP (1) | EP3078586B1 (en) |
| CN (1) | CN106043662A (en) |
| ES (1) | ES2669493T3 (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3095688B1 (en) * | 2015-05-20 | 2017-10-04 | Airbus Operations GmbH | A pressure bulkhead for an aircraft fuselage |
| EP3095689B1 (en) | 2015-05-20 | 2017-10-04 | Airbus Operations GmbH | A pressure bulkhead for an aircraft fuselage |
| FR3040686B1 (en) * | 2015-09-08 | 2018-09-07 | Airbus Operations Sas | REAR AIRCRAFT PART COMPRISING A VERTICAL STABILIZER WHOSE STRUCTURE FORMING HOUSING INCLUDES A LOWER PART IN THE FUSELAGE |
| CN107194079B (en) * | 2017-05-25 | 2020-12-15 | 中国商用飞机有限责任公司 | Pixel subdivision load transfer method and system |
| EP3584152B1 (en) * | 2018-06-19 | 2023-06-07 | Airbus Operations, S.L.U. | Method for manufacturing a multi-spar box with a continuous skin upper shell of a tail cone section for a rear end of an aircraft and a composite assembly |
| ES2881952T3 (en) | 2018-07-23 | 2021-11-30 | Airbus Operations Slu | Composite airframe assembly and procedures and devices for its manufacture |
| CN109720544A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of large water aircraft fuselage vertical fin docking structure |
| EP3653490B1 (en) * | 2018-11-16 | 2024-01-03 | Airbus Operations, S.L.U. | Frame assembly for a rear section of an aircraft and rear section of an aircraft comprising said frame assembly |
| US11370523B2 (en) * | 2020-05-27 | 2022-06-28 | The Boeing Company | Aircraft with multi spar box connection to fuselage |
| US11511846B2 (en) | 2020-05-27 | 2022-11-29 | The Boeing Company | Aircraft with multi spar box connection to fuselage |
| US11655019B2 (en) | 2020-05-27 | 2023-05-23 | The Boeing Company | Method and system for coupling a vertical stabilizer to an aircraft fuselage |
| US20220048610A1 (en) * | 2020-08-12 | 2022-02-17 | The Boeing Company | Cfrp fuselage frame with securement to vertical tail fin |
| US11932398B2 (en) | 2020-08-24 | 2024-03-19 | The Boeing Company | Horizontal stabilizer assembly for an aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4448372A (en) * | 1981-09-30 | 1984-05-15 | The Boeing Company | Aircraft vertical fin-fuselage structural integration system |
| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| US20050151018A1 (en) * | 2003-12-29 | 2005-07-14 | Airbus Deutschland Gmbh | Rudder unit connection |
| KR100843170B1 (en) * | 2002-09-12 | 2008-07-02 | 한국항공우주산업 주식회사 | Installing structure for the vertical tail of airplane |
| US20100148000A1 (en) * | 2008-12-17 | 2010-06-17 | Airbus Espana S.L.. | Aircraft horizontal stabilizer surface |
| EP2098448A4 (en) * | 2006-11-29 | 2012-08-08 | Airbus Operations Sl | Composite pressure bulkhead for aircraft |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3666211A (en) * | 1970-03-12 | 1972-05-30 | Mc Donnell Douglas Corp | Trijet aircraft |
| EP1550606B1 (en) * | 2003-12-29 | 2008-12-10 | Airbus Deutschland GmbH | Vertical stabilizer attachment |
| DE102006027707A1 (en) * | 2006-06-14 | 2007-12-20 | Airbus Deutschland Gmbh | Tail structure for e.g. spacecraft, has separation unit for pressure-tight locking of trunk section, where separation unit is coupled with support construction and with trunk section for forming force-flow path |
| FR2975666B1 (en) * | 2011-05-23 | 2014-01-17 | Airbus Operations Sas | AIRCRAFT WITH REVERSE REAR PART |
| US9162748B2 (en) * | 2011-07-22 | 2015-10-20 | Textron Innovations Inc. | Aft-loading aircraft with twin T-tail assembly |
| US8746616B2 (en) * | 2011-10-19 | 2014-06-10 | The Boeing Company | Mid-wing multi-deck airplane |
| ES2702873T3 (en) * | 2013-12-31 | 2019-03-06 | Airbus Operations Sl | Aircraft with a trimable horizontal stabilizer that has the pivoting elements on its front side |
| FR3040686B1 (en) * | 2015-09-08 | 2018-09-07 | Airbus Operations Sas | REAR AIRCRAFT PART COMPRISING A VERTICAL STABILIZER WHOSE STRUCTURE FORMING HOUSING INCLUDES A LOWER PART IN THE FUSELAGE |
-
2015
- 2015-04-08 EP EP15382169.9A patent/EP3078586B1/en active Active
- 2015-04-08 ES ES15382169.9T patent/ES2669493T3/en active Active
-
2016
- 2016-04-04 US US15/089,675 patent/US10046848B2/en active Active
- 2016-04-05 CN CN201610206268.XA patent/CN106043662A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4448372A (en) * | 1981-09-30 | 1984-05-15 | The Boeing Company | Aircraft vertical fin-fuselage structural integration system |
| CN1177561A (en) * | 1996-10-07 | 1998-04-01 | 王新云 | Prestressing structure of aircraft and making method thereof |
| KR100843170B1 (en) * | 2002-09-12 | 2008-07-02 | 한국항공우주산업 주식회사 | Installing structure for the vertical tail of airplane |
| US20050151018A1 (en) * | 2003-12-29 | 2005-07-14 | Airbus Deutschland Gmbh | Rudder unit connection |
| EP2098448A4 (en) * | 2006-11-29 | 2012-08-08 | Airbus Operations Sl | Composite pressure bulkhead for aircraft |
| US20100148000A1 (en) * | 2008-12-17 | 2010-06-17 | Airbus Espana S.L.. | Aircraft horizontal stabilizer surface |
Also Published As
| Publication number | Publication date |
|---|---|
| US20160297510A1 (en) | 2016-10-13 |
| ES2669493T3 (en) | 2018-05-28 |
| EP3078586A1 (en) | 2016-10-12 |
| EP3078586B1 (en) | 2018-02-21 |
| US10046848B2 (en) | 2018-08-14 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161026 |
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| WD01 | Invention patent application deemed withdrawn after publication |